Circumference splice for joining shell structures

• US 8,960,606 B2
• Filed: 10/31/2012
• Issued: 02/24/2015
• Est. Priority Date: 10/31/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Diep, Paul, Dopker, Bernhard
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US13/665,664
• Publication Number:
  US 20140117157A1
• Time in Patent Office: 846 Days
• Field of Search: 244/131, 244/132, 244/120, 244/119, 244/117.R
• US Class Current: 244/132
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: B64C 1/069 Joining arrangements therefor
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: Y10T 29/49622 Vehicular structural member making

Abstract

The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.

Claims

1. A shell structure splice comprising:

a first panel comprising a first edge;

a second panel comprising a second edge, said second edge positioned in edgewise alignment with said first edge of said first panel to form a splice joint;

a first stringer connected to said first panel and spaced away from said first edge of said first panel;

a second stringer connected to said second panel and spaced away from said second edge of said second panel;

a strap connected to said first panel and said second panel bridging said splice joint, said strap comprising a top surface opposite said first panel and said second panel, a flat bottom surface contacting said first panel and said second panel, a first side, and a second side opposite said first side, said top surface defining a flat middle region disposed over said splice joint, a first tapered region extending from proximate said middle region to proximate said first side, and a second tapered region extending from proximate said middle region to proximate said second side;

a first fitting comprising a first flat section connected to said first stringer and extending to proximate said first side of said strap and a first tapered section extending from proximate said first side to proximate said middle region of said strap and connected to said first tapered region of said strap; and

a second fitting comprising a second flat section connected to said second stringer and extending to proximate said second side of said strap and a second tapered section extending from proximate said second side to proximate said middle region of said strap and connected to said second tapered region of said strap,

wherein said first fitting and said second fitting are spaced apart by said middle region of said strap.

2. The splice of claim 1 wherein at least a portion of said first tapered region of said strap is positioned between said first tapered section of said first fitting and said first panel.

3. The splice of claim 1 wherein at least a portion of said second tapered region of said strap is positioned between said second tapered section of said second fitting and said second panel.

4. The splice of claim 1 wherein said first panel and said second panel are fuselage sections of an aircraft.

5. The splice of claim 1 wherein said first tapered region slopes downwardly from said middle region to said first side;

and,

wherein said second tapered region slopes downwardly from said middle region to said second side.

6. The splice of claim 1 wherein said first flat section of said first fitting is attached to said first panel and said second flat section of said second fitting is attached to said second panel.

7. The splice of claim 1 wherein said first flat section of said first fitting and said second flat section of said second fitting each comprises a first longitudinal member and a spaced apart second longitudinal member, wherein a portion of said first stringer fits between said first longitudinal member and said second longitudinal member of said first flat section, and wherein a portion of said second stringer fits between said first longitudinal member and said second longitudinal member of said second flat section.

8. The splice of claim 1 wherein said strap comprises a composite material.

9. The splice of claim 8 wherein said strap further comprises a tapered internal structure surrounded by a carbon fiber reinforced plastic.

10. The splice of claim 1 further comprising a frame attached to said middle region of said strap and disposed between said first fitting and said second fitting.

11. A splice for joining a shell structure comprising a first panel, a first stringer connected to said first panel, a second panel aligned with said first panel, and a second stringer connected to said second panel and aligned with said first stringer, said splice comprising:

a strap to bridge said first panel and said second panel, said strap comprising a top surface, a bottom surface, a first side, and a second side opposite said first side, said top surface defining a flat middle region, a flat first tapered region extending from proximate said middle region to proximate said first side, and a flat second tapered region extending from said middle region to proximate said second side;

a first fitting associated with said first stringer, said first fitting comprising a first tapered section contacting at least a portion of said first tapered region of said strap and extending from proximate said middle region to proximate said first side of said strap and a first flat section extending beyond said first side of said strap; and

,

a second fitting associated with said second stringer, said second fitting comprising a second tapered section contacting at least a portion of said second tapered region of said strap and extending from proximate said middle region to proximate said second side of said strap and a second flat section extending beyond said second side of said strap,

wherein said first fitting and said second fitting are spaced apart by said middle region of said strap.

12. The splice of claim 11 further comprising a frame contacting said middle region of said strap and disposed between said first fitting and said second fitting.

13. The splice of claim 11 wherein said strap comprises a composite material.

14. The splice of claim 13 wherein said strap further comprises a tapered internal structure surrounded by a carbon fiber reinforced plastic.

15. A method of joining a shell structure, said method comprising the steps of:

positioning a first panel comprising a first stringer and a second panel comprising a second stringer of said shell structure in edgewise alignment to form a splice joint;

positioning a strap between said first stringer and said second stringer bridging said splice joint, said strap comprising a top surface opposite said first panel and said second panel, a flat bottom surface contacting said first panel and said second panel, a first side, and a second side opposite said first side, said top surface defining a flat middle region disposed over said splice joint, a first tapered region extending from proximate said middle region to proximate said first side, and a second tapered region extending from proximate said middle region to proximate said second side;

connecting said strap to said first panel and said second panel;

positioning a first fitting relative to said first stringer and said strap, said first fitting comprising a first flat section and a first tapered section;

connecting said first tapered section of said first fitting to said first tapered region of said strap;

connecting said first flat section of said first fitting to at least one of said first panel and said first stringer;

positioning a second fitting relative to said second stringer and said strap, said second fitting comprising a second flat section and a second tapered section;

connecting said second tapered section of said second fitting to said second tapered region of said strap; and

connecting said second flat section of said second fitting to at least one of said second panel and said second stringer,

wherein said first fitting and said second fitting are spaced apart by said middle region of said strap.

16. The method of claim 15 wherein positioning said first fitting relative to said first stringer and said first strap comprises:

contacting said first flat section of said first fitting and said first stringer, said first flat section extending to proximate said first side of said strap; and

contacting said first tapered section and at least a portion of said first tapered region of said strap, said first tapered section extending from proximate said first side to proximate said middle region of said strap, and

wherein positioning said second fitting relative to said second stringer and said first strap comprises;

contacting said second flat section of said second fitting and said second stringer, said second flat section extending to proximate said second side of said strap; and

contacting said second tapered section and at least a portion of said second tapered region of said strap, said second tapered section extending from proximate said second side to proximate said middle region of said strap.

17. The method of claim 15 further comprising the steps of:

positioning a frame on said middle region of said strap between said first fitting and said second fitting; and

connecting said frame to said middle region of said strap.

18. The method of claim 17 wherein said first panel and said second panel are fuselage sections of an aircraft.

19. The method of claim 17 wherein at least one of said strap, said first fitting, said second fitting, and said frame comprise a composite material.